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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal of the Korean Society of Propulsion Engineers
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Journal DOI :
The Korean Society of Propulsion Engineers
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Volume & Issues
Volume 19, Issue 6 - Dec 2015
Volume 19, Issue 5 - Oct 2015
Volume 19, Issue 4 - Aug 2015
Volume 19, Issue 3 - Jun 2015
Volume 19, Issue 2 - Apr 2015
Volume 19, Issue 1 - Feb 2015
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Internal Flow Characteristics of Simulated Dual Pulse Rocket Motor by Using the Hot Gas and Cold Gas
Cho, Kihong ; Park, Jungho ; Kim, Euiyong ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 2, 2015, Pages 1~8
DOI : 10.6108/KSPE.2015.19.2.001
Dual pulse rocket motor is a variant of solid rocket motor with two propellant grain separated by a pulse separation device. The major performance of such a rocket motor is influenced by the change in the hole area of pulse separation device to nozzle throat area ratio. In this study, we performed flow analysis to investigate the internal flow characteristics according to the pulse separation device hole area to nozzle throat area ratio change. Gases used flow analysis were used combustion gas of HTPB/AP composite propellant and nitrogen gas. Flow analysis results of the dual pulse rocket motor were validated by comparison with experimental results of pneumatics. Commercial CFD code ANSYS FLUENT 14.5 is used in this study to simulate flow analysis.
Pressure Guidance and Thrust Allocation Law of Solid DACS
Park, Iksoo ; Hong, Seokhyun ; Ki, Taeseok ; Park, Jungwoo ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 2, 2015, Pages 9~16
DOI : 10.6108/KSPE.2015.19.2.009
The control law for simultaneous pressure and thrust control of solid DACS(Divert Attitude Control System) is suggested. To regulate the two variables effectively, the control structure of sequential loop closer is applied to the system considering the physical characteristics of each variable and the weighted pseudo-inverse method is suggested to allocate effective command for indeterminate system. Also, the pressure guidance law for safe and high acceleration is applied to the homing stage to verify the effectiveness of the command distribution.
Design of Control Method for ON/OFF Type Actuation System Considering Actuation Limit
Park, Jungwoo ; Park, Iksoo ; Park, Dongchang ; Hwang, Kiyoung ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 2, 2015, Pages 17~28
DOI : 10.6108/KSPE.2015.19.2.017
In this paper, it is accomplished to design a control method for such an actuation system of simplified ON/OFF mechanism with actuation command limit. First of all, based on experimental data, the modeling works for nonlinear/linear actuation dynamics are performed, which are govern by PWM command as a control input. Using the linearized model, a classical PI control method is designed to satisfy the aimed control performance requirements, and a control algorithm is proposed to realize the required control performance in the effective control region through resolving the issue for the PWM command limit which reduces the control performance. Finally, through control simulations, the design method is verified and the corresponding control performance improvement is evaluated.
Numerical Analysis of Detonation of Kerosene-Air Mixture and Solid Structure
Lee, Younghun ; Gwak, Min-Cheol ; Yoh, Jai-Ick ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 2, 2015, Pages 29~37
DOI : 10.6108/KSPE.2015.19.2.029
This paper presents a numerical investigation on detonation of a kerosene-air mixture in the copper tube and the structural response associated with combustion instability in liquid rocket engine. A single step Arrehnius rate law and Johnson-Cook strength model are used to describe the chemical reaction of kerosene-air mixture detonation and the plastic deformation of the copper tube. The changes of flow field and tube stress which are induced by plastic deformation, are investigated on the different tube thicknesses and nozzle configurations.
A Study on Design and Performance of an Ejector Using Cold Gas
Yu, Isang ; Kim, Taewoan ; Kim, Minseok ; Ko, Youngsung ; Kim, Sunjin ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 2, 2015, Pages 38~45
DOI : 10.6108/KSPE.2015.19.2.038
This paper describes an ejector design technique which used for simulating low pressure environment corresponding to high altitude. Also the ejector performance characteristics was investigated according to performance and geometric variables by cold gas flow test. Entrainment ratio, compression ratio and expansion ratio were designated as performance variables and an ejector gap ratio was designated as a geometric variable. A relationship between the performance variables to predict the ejector performance was identified and it was confirmed that the performance variables have much more effective than the ejector gap ratio through the ejector cold gas flow test.
Explosive Accidents and Safe Handling of an Experimental Liquid Rocket Engine Using Nitrous Oxide as Oxidizer
Choi, Songyi ; Park, Sukyoung ; Lee, Donggun ; Kim, Dohun ; Koo, Jaye ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 2, 2015, Pages 46~54
DOI : 10.6108/KSPE.2015.19.2.046
Nitrous oxide is known as green and safe propellant, and can be supplied by its own vapor pressure. So, many liquid propulsion research institutes and university laboratories use nitrous oxide as oxidizer of experimental liquid rocket engine. However, the unknown explosions occurred twice during hot fire experiments using subscale ethanol/nitrous oxide thruster. In this paper, we surmised that the explosions were caused by the decomposition of nitrous oxide in the injector body and the recondensation of nitrous oxide. Improvement and the safe handling methods are suggested.
A Computational Study on Cooling Analysis of the Flame Deflector for the 75 tonf Class Propulsion Test Facility
Moon, Seong-Mok ; Cho, Nam-Kyung ; Kim, Seong-Lyong ; Jun, Sung-Bok ; Lee, Kyoung-Hoon ; Kim, Dong-Hwan ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 2, 2015, Pages 55~64
DOI : 10.6108/KSPE.2015.19.2.055
In this study, a 3-D flame cooling analysis is conducted to examine thermal safety for the flame deflector of the 75 tonf class propulsion test facility, and the safe discharge of the exhaust gas is assessed by using numerical results. The Mixture multiphase model is adopted for the simulation of heat transfer and phase exchange process between flame and cooling water, and the computational study using the single species unreacted model for the exhaust plume is carried out for the flame cooling. Numerical analysis predicts maximum temperature on the flame deflector wall for different water flow rates, and evaluates the safe minimum flow rate of water corresponding to the fire-resistant temperature for concrete.
Performance Test of a 7 tonf Liquid Rocket Engine Turbopump
Kwak, Hyun Duck ; Kim, Dae-Jin ; Kim, Jin-Sun ; Kim, Jinhan ; Noh, Jun-Gu ; Park, Pyun-Goo ; Bae, Jun-Hwan ; Shin, Ju-Hyun ; Yoon, Suck-Hwan ; Lee, Hanggi ; Jeon, Seong-Min ; Jeong, Eunhwan ; Choi, Chang-Ho ; Hong, Soon-Sam ; Kim, Seong-Lyong ; Kim, Seung-Han ; Han, Yeong-Min ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 2, 2015, Pages 65~72
DOI : 10.6108/KSPE.2015.19.2.065
Performance tests of a turbopump for the developing 7-tonf liquid rocket engine were conducted. The performance of turbopump components and their power matching were measured and examined firstly under the LN2 and water environment. In the real propellant(LOX and kerosene) environment tests, design and off-design performances of turbopump were fully verified. During the off-design tests, turbopump running time was set the same as engine operating time and pump inlet pressure were set lower than nominal operating value in order to investigate pump suction capability. It have been verified that subject turbopump satisfies required performance - flow rate, head, suction performance and operational time - in the operating regime of developing liquid rocket engine.
The Review of Saturn V 1st Stage (S-IC) Propulsion System
Hong, Yonggi ; Kim, Cheulwoong ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 2, 2015, Pages 73~80
DOI : 10.6108/KSPE.2015.19.2.073
It had been almost a half century since Apollo Mission was ended. However, in these days, a lot of researches are being conducted for restoration and making improvements in technologies used in Saturn V rocket`s development. This study reviews the first stage of Saturn V rocket(S-IC), from development history to technologies in various subsystems such as engine purge system, POGO suppression system, hydraulic and pneumatic control system, propellant dispersion system, telemetry system and retrorocket system. Understandings of S-IC stage`s operation systems would be helpful in understanding of launch vehicle system and reduction of time and cost in future development process.
Improvement of Fuel Economy in a Diesel Engine by Application of Low Pressure EGR System
Kim, Yongrae ; Lee, Yonggyu ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 2, 2015, Pages 81~87
DOI : 10.6108/KSPE.2015.19.2.081
LP(low pressure)-EGR system was investigated to evaluate its potential on fuel economy improvement and NOx emission reduction in a diesel engine. A diesel engine was tested for the evaluation of LP-EGR system at both of steady-state and transient test. For a transient test, control logic for LP-EGR valve operation was developed and a NEDC mode test was conducted by using a vehicle status simulation test. The steady-state results showed that LP-EGR system can reduce more NOx emission or fuel consumption comparing to the conventional HP(high pressure)-EGR. From the NEDC mode test, this LP-EGR system showed a possibility to improve fuel economy without a penalty of emissions.